EP0186609B1 - Dispositif de mesure de la température - Google Patents

Dispositif de mesure de la température Download PDF

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Publication number
EP0186609B1
EP0186609B1 EP85630221A EP85630221A EP0186609B1 EP 0186609 B1 EP0186609 B1 EP 0186609B1 EP 85630221 A EP85630221 A EP 85630221A EP 85630221 A EP85630221 A EP 85630221A EP 0186609 B1 EP0186609 B1 EP 0186609B1
Authority
EP
European Patent Office
Prior art keywords
stream
strut
temperature
tube
gaseous stream
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
EP85630221A
Other languages
German (de)
English (en)
Other versions
EP0186609A2 (fr
EP0186609A3 (en
Inventor
Joseph Michael Kokoszka
Rocco Michael Tommasini
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP0186609A2 publication Critical patent/EP0186609A2/fr
Publication of EP0186609A3 publication Critical patent/EP0186609A3/en
Application granted granted Critical
Publication of EP0186609B1 publication Critical patent/EP0186609B1/fr
Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K13/00—Thermometers specially adapted for specific purposes
    • G01K13/02—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow

Definitions

  • This invention relates to temperature probes and particularly to the type of temperature probes utilized on gas turbine engines.
  • the temperature sensor monitors this condition and relays a signal when either the temperature exceeds a predetermined limit or the rate of temperature change is at an undesirable value.
  • This condition is exemplified in the graph depicted in Fig. 6 where the curve labeled A represents the signal produced by a probe incorporating the invention and curve B represents a signal produced by a probe that includes an inlet similar to the one described in US-A-4,433,584. The tests represented by this graph were done concurrently so that conditions for both probes were identical. As is apparent, the rate of change for the sensor producing curve B was too slow to be of any value, as a "hot start" would occur before corrective action could be manifested.
  • the object of this invention is to provide a temperature probe installed in a strut, and a gas turbine engine having a strut with such a temperature probe that obviates the problems noted above and accurately measures the temperature in a stream whose direction varies over a wide range of operating conditions including operating conditions below idle when used in a gas turbine engine.
  • a temperature probe for measuring the temperature of a gaseous stream whose direction varies, said temperature probe being installed in a strut having a leading edge disposed in said gaseous stream, and said temperature probe having a temperature measuring element mounted in a cavity in said strut and a passageway in said strut leading a portion of said gaseous stream from said leading edge to said temperature measuring element and to a discharge port located at the side of said strut where the static pressure is at a value lower than the value of the pressure adjacent said leading edge, characterized by means for obtaining a free stream velocity of said gaseous stream in said passageway, said means including a tube projecting from said leading edge and communicating with said passageway, the free end of said tube being scarfed in the direction of said gaseous stream.
  • a gas turbine engine having turbine blades being powered by a fluid working medium operating over a range of rotational speeds, a strut mounted in proximity to said turbine blades disposed in the stream of said fluid working medium discharging from said turbine blades, means for measuring the temperature of said discharging stream including a temperature sensing element mounted in a cavity of said strut, a passageway leading from the leading edge of said strut to a low static pressure station of said strut through said cavity for leading a portion of said discharging stream over said temperature sensing element, characterized by a tube having a passage communicating with said passageway and having a central axis mounted in said strut and projecting into said discharging stream, said tube having a free end being scarfed in the direction of said discharging stream, the direction of the absolute velocity of said discharging stream being in coincidence with said central axis at a given predetermined rotational speed of said gas turbine engine and the absolute velocity of said discharging stream being perpendicular
  • the probe of the invention is designed to provide a fixed stagnation point at the throat of the probe's inlet which provides satisfactory indication of temperature throughout the entire operating envelope of the engine. With the tube projecting beyond the leading edge of the strut and being scarfed in the direction of the flow of the engine's working medium any change in direction of flow of the engine's working medium will have substantially no effect on the flow of that medium passing through the probe.
  • temperature probe of this invention is described in its preferred embodiment to being attached to the leading edge of a strut of a gas turbine engine, the invention as will be obvious to one ordinarily skilled in this art has application wherever temperature accuracy is desired and the direction of the fluid stream being sensed varies.
  • Fig. 2 shows a plurality of inlets 30 extending from the leading edge of a strut 32 suitably mounted in the engine's exhaust case 34.
  • the engine exhaust case 34 is generally circular in shape and carries a plurality of such struts circumferentially spaced internally of the case.
  • the exhaust case 34 defines an annular space 35 through which the engines fluid working medium discharging from the turbine bucket 36 of the turbine rotor 38 flows.
  • the inlet 30 serves to admit the engine's working medium internally of the strut to pass over the temperature measuring element 40 which may be of any commercially available suitable design that is capable of operating and sensing temperature in this environment.
  • the inlet 30 comprises a cylindrically shaped tube 31 mounted in a drilled hole 37 in the leading edge 42 of the strut 32 and the internal passageway 44 communicating with the drilled passage 46 extending from drilled hole 37.
  • Drilled passage 46 communicates with the vertically extending passageway 48 which houses the temperature sensors 56, there being one sensor for each inlet.
  • the drilled passageway 50 on the suction side of strut 32 is judiciously located in a point where the static pressure along the surface 52 is at a low value.
  • the inlet part of the passageway 46 provides satisfactory temperature readings for above idle but unsatisfactory readings below idle.
  • FIG. 4 The vector diagram of Fig. 4 illustrates the conditions of the fluid flowing through the turbine bucket for speeds above and below engine idle speeds.
  • the inlet 30 is scarfed in the direction of flow, scarf meaning that the end of tube 31 is truncated relative to the tube's centerline.
  • the degree of scarfing and the dimensions of the inlet and outlet are predicated on having the velocity through the probe bear a relationship to the free stream velocity.
  • the inlet throat should be at the stagnation pressure of the gaseous stream flowing through the strut and the bleed port should he at a station evidencing the desired reduced static pressure.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Measuring Temperature Or Quantity Of Heat (AREA)

Claims (3)

  1. Sonde de température permettant de mesurer la température d'un courant gazeux dont la direction varie, cette sonde de température étant installée dans une entretoise (32) ayant un bord d'attaque (42) disposé dans le courant gazeux, cette sonde de température comportant un élément de mesure de température (56) monté dans une cavité (48) de l'entretoise (32) et un passage (46,50) dans l'entretoise (32) conduisant une portion du courant gazeux, à partir du bord d'attaque (42), vers l'élément de mesure de température (56) et vers un orifice de sortie disposé du côté de l'entretoise (32) où la pression statique est à une valeur inférieure à la valeur de la pression au voisinage du bord d'attaque (42), caractérisée en ce qu'elle comprend des moyens permettant d'obtenir une vitesse d'écoulement libre du courant gazeux dans le passage (46,50), ces moyens comprenant un tube (31) faisant saillie à partir du bord d'attaque (42) et communiquant avec ledit passage (46,50), l'extrémité libre dudit tube (31) étant biseautée dans la direction du courant gazeux.
  2. Sonde de température selon la revendication 1, caractérisée en ce que l'angle de l'extrémité biseautée du tube (31) est une fonction de la direction d'écoulement du courant gazeux de sorte que l'axe du tube (31) soit orienté à l'alignement avec le courant gazeux pour un niveau de pression donné du courant gazeux et que le plan de la face d'entrée du tube (31) soit perpendiculaire à la direction du courant gazeux pour un niveau de pression inférieur du courant gazeux.
  3. Turbomoteur comportant des ailettes de turbine (36) propulsées par un fluide de travail et fonctionnant dans une gamme de vitesses de rotation, une entretoise (32) montée à proximité des ailettes de turbine (36) et disposée dans le courant du fluide de travail déchargé à partir des ailettes de turbine (36), des moyens de mesure de la température du courant déchargé comprenant un élément de mesure de température (56) monté dans une cavité (48) de l'entretoise (32), un passage (46,50) conduisant du bord d'attaque (42) de l'entretoise (32) vers un endroit à faible pression statique de l'entretoise (32), à travers la cavité (48), pour conduire une portion du courant déchargé sur l'élément de mesure de température (56), caractérisé en ce qu'il comporte un tube (31) comprenant un passage interne (44) en communication avec le passage (46,50), ayant un axe central monté dans l'entretoise (32) et faisant saillie dans le courant déchargé, ce tube (31) ayant une extrémité libre biseautée en direction du courant déchargé, la direction de la vitesse absolue du courant déchargé étant en coïncidence avec ledit axe central pour une vitesse de rotation prédéterminée du turbomoteur et la vitesse absolue du courant déchargé étant perpendiculaire à un plan coïncidant avec la face de l'extrémité libre du tube (31) faisant saillie dans le courant déchargé, pour une vitesse réduite du turbomoteur.
EP85630221A 1984-12-13 1985-12-12 Dispositif de mesure de la température Expired EP0186609B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US06/681,395 US4605315A (en) 1984-12-13 1984-12-13 Temperature probe for rotating machinery
US681395 1984-12-13

Publications (3)

Publication Number Publication Date
EP0186609A2 EP0186609A2 (fr) 1986-07-02
EP0186609A3 EP0186609A3 (en) 1988-04-13
EP0186609B1 true EP0186609B1 (fr) 1991-06-26

Family

ID=24735105

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85630221A Expired EP0186609B1 (fr) 1984-12-13 1985-12-12 Dispositif de mesure de la température

Country Status (4)

Country Link
US (1) US4605315A (fr)
EP (1) EP0186609B1 (fr)
JP (1) JPH068759B2 (fr)
DE (2) DE3583330D1 (fr)

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IL84611A (en) * 1987-11-26 1991-11-21 Ardon Gador Apparatus and method for protection against heat
DE4025314C2 (de) * 1990-08-09 1998-04-09 Bayerische Motoren Werke Ag Meßverfahren und Vorrichtungen zur Ermittlung von Meßdaten für die Temperaturverteilung und für die Berechnung von Strömungsgeschwindigkeitsvektoren über eine ungleichförmig durchströmte ebene Fläche
FR2680872A1 (fr) * 1991-09-02 1993-03-05 Auxitrol Sa Sonde pour la mesure de parametres physiques d'un flux de fluide.
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US6170338B1 (en) 1997-03-27 2001-01-09 Rosemont Inc. Vortex flowmeter with signal processing
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US6609431B1 (en) 2000-09-29 2003-08-26 Xellogy, Inc. Flow measuring device based on predetermine class of liquid
JP3749135B2 (ja) * 2001-03-13 2006-02-22 横河電子機器株式会社 温度測定装置
US20040114665A1 (en) * 2002-12-12 2004-06-17 Sun Park Cantilevered thermocouple rake
US6857776B2 (en) 2002-12-12 2005-02-22 Ametek, Inc. Connectorized high-temperature thermocouple
US20040114666A1 (en) * 2002-12-17 2004-06-17 Hardwicke Canan Uslu Temperature sensing structure, method of making the structure, gas turbine engine and method of controlling temperature
ITMI20032586A1 (it) * 2003-12-23 2005-06-24 Nuovo Pignone Spa Sistema di montaggio di una termocoppia per una turbina a gas
US7111982B1 (en) 2004-01-30 2006-09-26 Swonger Jr Karl William Combined temperature and pressure probe for a gas turbine engine
WO2005095902A1 (fr) 2004-03-25 2005-10-13 Rosemount Inc. Mesure simplifiee des proprietes de fluides
GB0510440D0 (en) * 2005-05-21 2005-06-29 Rolls Royce Plc An instrumentation rake
JP4672565B2 (ja) * 2006-02-06 2011-04-20 三菱重工業株式会社 温度計測装置、燃焼監視装置、及び、ガスタービン
US7527471B2 (en) * 2006-07-31 2009-05-05 General Electric Company Stator vane and gas turbine engine assembly including same
US8784051B2 (en) 2008-06-30 2014-07-22 Pratt & Whitney Canada Corp. Strut for a gas turbine engine
US20140182292A1 (en) * 2012-12-29 2014-07-03 United Technologies Corporation Integral instrumentation in additively manufactured components of gas turbine engines
FR3012169B1 (fr) 2013-10-21 2018-01-12 Safran Aircraft Engines Pale instrumentee
US20150114006A1 (en) * 2013-10-29 2015-04-30 General Electric Company Aircraft engine strut assembly and methods of assembling the same
EP3102806B1 (fr) * 2014-02-05 2020-09-09 United Technologies Corporation Capteur de pression pour turbine à gaz
US9856743B2 (en) * 2014-05-28 2018-01-02 Safran Aircraft Engines Instrumented flow passage of a turbine engine
FR3038981A1 (fr) * 2015-07-13 2017-01-20 Snecma Dispositif de mesure de grandeurs aerodynamiques destine a etre place dans une veine d'ecoulement d'une turbomachine
EP3363996B1 (fr) * 2017-02-16 2020-04-29 Ansaldo Energia Switzerland AG Agencement d'aube et moteur à turbine à gaz correspondant
BE1025194B1 (fr) * 2017-05-05 2018-12-07 Safran Aero Boosters S.A. Capteur de turbulences dans un compresseur de turbomachine
FR3066779B1 (fr) * 2017-05-26 2020-04-03 Safran Aircraft Engines Dispositif de mesure de parametres d'un flux aerodynamique pour pale de turbomachine, pale et organe de turbomachine equipes dudit dispositif de mesure
FR3072169B1 (fr) * 2017-10-09 2019-10-11 Safran Aircraft Engines Dispositif de mesure d'au moins un parametre d'un flux aerodynamique d'une turbomachine equipe d'un moyen d'amortissement vibratoire et veine de turbomachine equipee d'un tel dispositif
US10598041B2 (en) * 2017-10-20 2020-03-24 United Technologies Corporation Inlet performance measurement system for gas turbine engine
KR102038555B1 (ko) * 2018-03-15 2019-10-30 두산중공업 주식회사 가스터빈 및 가스터빈의 제어방법
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US11230927B2 (en) * 2019-06-03 2022-01-25 Raytheon Technologies Corporation Vane airfoil shapes for embedded members
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KR102295046B1 (ko) * 2020-02-24 2021-08-30 두산중공업 주식회사 스테이터 구조 및 이를 포함하는 가스터빈
US12092025B2 (en) * 2021-12-22 2024-09-17 Unison Industries, Llc Turbine engine exhaust gas temperature sensor
US11821811B2 (en) * 2022-02-04 2023-11-21 Pratt & Whitney Canada Corp. Fluid measurement system for an aircraft gas turbine engine and method for operating same
US11891902B2 (en) * 2022-04-15 2024-02-06 Pratt & Whitney Canada Corp. Fluid measurement system and method for operating same
CN115219209B (zh) * 2022-06-15 2023-11-10 中国船舶重工集团公司第七0三研究所 一种可提拉式高温涡轮出口气流角测量装置设计方法
FR3145982A1 (fr) * 2023-02-17 2024-08-23 Airbus Râteau de mesure de pression comportant un bord d’attaque rapporté.
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Also Published As

Publication number Publication date
DE186609T1 (de) 1986-12-18
EP0186609A2 (fr) 1986-07-02
JPH068759B2 (ja) 1994-02-02
DE3583330D1 (de) 1991-08-01
US4605315A (en) 1986-08-12
EP0186609A3 (en) 1988-04-13
JPS61144540A (ja) 1986-07-02

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